Research On High Speed Static Aeroelastic Model Design Of High-Aspect-Ratio Wing

High-aspect-ratio&aft-sweep wing configuration, advanced structure designmethods and composite material techniques are applied in designing modern largeaircrafts, as a result, the weight is much less and the structural flexibility is much larger.The static aeroelastic concern is particularly significant. In order to study the impact ofstatic aeroelasticity of high-aspect-ratio wing, the corresponding static aeroelastic windtunnel tests should be conducted substantially.The subject of static aeroelastic test is to obtain the amount of deformation andaerodynamic forces by employing aeroelastic wind-tunnel-model in various tunneldynamic pressure(to simulate various attitude of the aircraft), to study the influence ofaeroelastic deformation on aerodynamic characteristics, and then, in the developing ofnew aircraft, to modify the rigid wind-tunnel-model experimental data and provide morereliable basis for wind tunnel/flight data correlation, or to validate and assess theaccuracy of computational aeroelastic codes.Compared with regular wind tunnel tests, there are two technical difficulties aboutstatic aeroelastic wind tunnel tests. One is the design and construction of the staticaeroelastic wind-tunnel-model. Another is the static aeroelastic wind tunnel testtechniques. The basic requirement of static aeroelastic wind-tunnel-model is to simulatethe geometrical shape as well as the distribution of the stiffness to maintain thestructural statics characteristic similarity and aerodynamic characteristic similaritybetween wind-tunnel-model and flight vehicle. Consequently, carrying out the researchon high speed static aeroelastic model design technique of high-aspect-ratio wing is ofparamount importance and meaningful to study the impact of static aeroelasticity onlarge aircraft, structural check and optimization.This work presents the design process of a high-aspect-ratio high speed staticaeroelastic research wing by structural optimization technology. The model design is aninverse structural design in specified structural flexibility influence coefficient. Maincontents are listed as follows:In the introduction, the origin and development of aeroelasticity are described, andthe three aspects of static aeroelasticity impact on aerodynamic characteristic of aircraftare summarized.In chapter two, the physical nature of static aeroelasticity is made clear by takingan airfoil as an example. The similarity parameters between an aircraft and scaled modelare developed by dimensional analysis and physical equations. And the application offinite element method in the structural analysis of high-aspect-ratio wing is introduced.In chapter three, the processes of static aeroelastic wind-tunnel-model design, the principles and methods of ground stiffness test are given in details. The structuraloptimization procedures are established by framework software Isight combined withthe structural finite element analysis tool MSC.NASTRAN.In chapter four, the structural finite element model of the static aeroelasticwind-tunnel-model was built by MSC.PATRAN, and the structural flexibility influencecoefficients are obtained by MSC.NASTRAN. Response surface approximationtechnique was used in the optimization. The ground stiffness tests were conducted toassess the structural characteristic of the model. The results show that the approachdeveloped in this paper is feasible.In the conclusion, the present work is summarized. Some proposals for futuredirection in the research are put forward.